Avionics instrument and mounting bracket

ABSTRACT

The present invention is an avionics instrument and mounting bracket. In particular, the present invention is directed to an avionics instrument that can be mounted in a variety of positions on an aircraft instrument panel. The mounting bracket preferably comprises a cylindrical interior and an exterior with squared sides and rounded corners. The bracket has an adjustment gap with first and second ports on opposing sides and an adjustment screw spanning the adjustment gap to adjust the tightness of the bracket. The front of the bracket preferably has four panel screw ports. The avionics instrument has a display panel mounted to a cylindrical electronics housing where the diameter of the housing is less than the length of the display panel. The display panel preferably has four positional modes of display and a control button for switching between the display modes. The cylindrical electronics housing is inserted into the bracket.

TECHNICAL FIELD

The present invention is an avionics instrument and mounting bracket. Inparticular, the present invention is directed to an avionics instrumentdisplay that can be mounted in a variety of positions on an instrumentpanel.

BACKGROUND ART

Standard instrument panels in aircraft often comprise pre-cut holes oftypical sizes, roughly 2 inches and 3 inches in diameter. Accordingly,after-market avionics instruments are often made to fit these pre-cutholes but are limited in how they can be positioned on the panel.Moreover, given the substantial heat generated by electronics in currentavionics, these instruments can become, inter alia, hot to the touchunless properly cooled with a fan or otherwise ventilated. The presentinvention provides an improved avionics instrument display that can bemounted to an aircraft panel in a variety of positions and kept coolerwithout the use of a fan.

SUMMARY OF THE INVENTION

The present invention is an avionics instrument and mounting bracket. Inparticular, the present invention is directed to an avionics instrumentthat can be mounted in a variety of positions on an aircraft instrumentpanel. The mounting bracket preferably comprises a cylindrical interiorand an exterior with squared sides and rounded corners. The bracket hasan adjustment gap with first and second ports on opposing sides and anadjustment screw spanning the adjustment gap to adjust the tightness ofthe bracket. The front of the bracket preferably has four panel screwports. The avionics instrument has a display panel mounted to acylindrical electronics housing where the diameter of the housing isless than the length of the display panel. The display panel preferablyhas four positional modes of display and a control button for switchingbetween the display modes. The cylindrical electronics housing isinserted into the bracket.

BRIEF DESCRIPTION OF THE DRAWINGS

The objects and features of the present invention, which are believed tobe novel, are set forth with particularity in the appended claims. Thepresent invention, both as to its organization and manner of operation,together with further objects and advantages, may best be understood byreference to the following description, taken in connection with theaccompanying drawings.

FIG. 1 is a front perspective view of a preferred embodiment of theavionics instrument portion of the invention;

FIG. 2 is a front perspective exploded view of four preferredembodiments of the avionics instruments installed in an aircraftinstrument panel in four different positional display modes, namely twolandscape and two portrait display modes;

FIG. 2 a is a front view of a preferred embodiment of the instrument ina first portrait display position showing first portrait display mode inthe display area;

FIG. 2 b is a front view of a preferred embodiment of the instrument ina first landscape display position showing first landscape display modein the display area;

FIG. 2 c is a front view of a preferred embodiment of the instrument ina second portrait display position showing second portrait display modein the display area;

FIG. 2 d is a front view of a preferred embodiment of the instrument ina second landscape display position showing second landscape displaymode in the display area;

FIG. 3 is a side view of a preferred embodiment of the inventioninstalled in a portrait display mode and held in place by a preferredembodiment of the mounting bracket;

FIG. 4 is a rear view of a preferred embodiment of the avionicsinstrument portion of the invention;

FIG. 5 is a front view of a preferred embodiment of the mounting bracketportion of the invention;

FIG. 6 is a side view of a preferred embodiment of the mounting bracketportion of the invention;

FIG. 7 is a side view of a preferred embodiment of the mounting bracketportion of the invention;

FIG. 8 is a diagram of a preferred embodiment of the avionicsinstrument; and,

FIG. 9 is a flow chart showing a preferred method for adjusting thedisplay alignment of the instrument.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

The following description is provided to enable any person skilled inthe art to make and use the invention and sets forth the best modescontemplated by the inventor of carrying out his invention. Variousmodifications, however, will remain readily apparent to those skilled inthe art, since the general principles of the present invention have beendefined herein specifically to provide an improved avionics instrumentand mounting bracket.

Referring now to FIG. 1, a preferred embodiment of the avionicsinstrument 10 is shown. The avionics instrument 10 shown has a displaypanel 20 mounted to a cylindrical electronics housing 30. The displaypanel 20 shown has a display area 22, a first control button 24(preferably the “STEP” button), a USB data port 26, and a second controlbutton 28 (preferably the “LF” button). The electronics for the avionicsinstrument 10 not related to the display panel 20 are preferablycontained within the cylindrical electronics housing 30.Data/Information from probes connected to the instrument (not shown) iscollected and/or analyzed within the cylindrical electronics housing 30.The data and analysis are then displayed in the display area 22 of thedisplay panel 20. FIG. 1 shows the instrument 10 in position to show aportrait display mode.

Referring now to FIG. 8, a diagram of a preferred embodiment of theinstrument 10 is shown. As stated above, the electronics for theinstrument are mostly contained within the cylindrical electronicshousing 30. Fuel flow and tachometer sensor inputs 32 are preferablyconnected directly to a central processing unit (CPU) 34. The CPU 34preferably has a built-in LCD controller such as an ARM9 or otherprocessor. Pressure sensor and thermocouple sensor inputs 32 arepreferably connected to the CPU 34 via an analog multiplexer 36 andanalog to digital converter 38. The analog to digital converter 38preferably has a 16-bit resolution or better.

As shown in FIG. 8, the cylindrical electronics housing 30 is attachedto the display panel 20. The display panel 20 preferably comprises adisplay panel 20 housing a backlight CCFL or LED with pulsewidthmodulation intensity control 23 and a color LCD module 25. The backlightCCFL or LED 23 and color LCD module 25 are connected to, and controlledby, the CPU 34. The color LCD module 25 preferably has a resolution ofat least 320×240 pixels (1/4 VGA) and preferably at least 65,536 colordepth. As shown in FIG. 8, the push button switches 24, 28 arepreferably connected to the CPU 34, as is the USB host port 26.

Referring back to FIG. 1, the cylindrical electronics housing 30preferably has a primary dimension, e.g. a diameter, that is less than3.0″ inches so that the housing 30 can fit into (and rotate within) mostopenings on common aircraft panels. Conversely, the display panel 20preferably has a primary dimension, e.g. a length, which is greater than3.0″ inches so the display panel 20 cannot pass through common aircraftpanel openings. Also, the display panel 20 is preferably mountedoff-center from the cylindrical electronics housing 30.

Moving on to FIG. 2, a preferred embodiment of the avionics instrument10 is shown in four different installation positions in a standardaircraft panel 100. Instrument 1 is shown in first portrait displayposition. The length of the display panel 20 is vertical and asignificant portion of the display panel 20 extends below the aircraftpanel opening 110. Instrument 3 is shown in first landscape displayposition. The length of the display panel 20 is horizontal and asignificant portion of the display panel 20 extends to the left of theaircraft panel opening 110 to which the instrument 3 is mounted.Instrument 2 is shown in second portrait display position. The length ofthe display panel 20 is vertical and a significant portion of thedisplay panel 20 extends above the aircraft panel opening 110.Instrument 4 is shown in second landscape display position. The lengthof the display panel 20 is horizontal and a significant portion of thedisplay panel 20 extends to the right of the aircraft panel opening 110to which the instrument 4 is mounted. Accordingly, there are preferablyfour different display positions for this embodiment of avionicsinstrument 10.

Moving now to FIGS. 2 a through 2 d, four preferred positional modes ofdisplay for the display panel 20 are shown. FIG. 2 a shows a preferredembodiment of the display 20 in first portrait display mode. The displayarea 22 shows data, information and analysis from the avionicsinstrument in a portrait mode and the length of the display 20 extendsbelow the diameter of the cylindrical electronics housing 30. FIG. 2 bshows a preferred embodiment of the display 20 in first landscapedisplay mode. The display area 22 shows data, information and analysisfrom the avionics instrument 10 in a landscape mode and the length ofthe display 20 extends to the left of the diameter of the cylindricalelectronics housing 30. FIG. 2 c shows a preferred embodiment of thedisplay 20 in second portrait display mode. The display area 22 showsdata, information and analysis from the avionics instrument 10 in aportrait mode and the length of the display 20 extends above thediameter of the cylindrical electronics housing 30. FIG. 2 d shows apreferred embodiment of the display 20 in second landscape portraitdisplay mode. The display area 22 shows data, information and analysisfrom the avionics instrument 10 in a landscape mode and the length ofthe display 20 extends to the right of the diameter of the cylindricalelectronics housing 30.

Preferred readouts in the display area 22 of the instrument 10 include,but are not limited to, RPM, a map, 4-9 EGT, 4-9 CHT, TIT (two), oiltemperature, oil pressure, OAT, volts, carburetor temperature, CDT, IAT,percentage of horse power, EGT SPAN, gallons of fuel consumed per hour,USD, REM, REQ, miles per gallon, and USB data. These readouts can bedisplayed in a number of different manners and formatted in a variety ofdifferent screen positions for each positional mode of display. Thus,each positional mode of display can have a variety of alternate screensdisplayed.

Moving on to FIG. 3, a side view of a preferred embodiment of theinvention is shown installed in an aircraft panel 100. The cylindricalelectronics housing 30 is inserted into the panel 100 at an opening 110.The user then selects the installation position for the display panel 20by rotating the instrument 10 in the opening 110. In FIG. 3, the firstportrait mode has been selected. The instrument is then held in itsinstallation position by a mounting bracket 40 (described below.) Theuser then connects one or more probes 50 (partially shown) from theaircraft engine to the cylindrical electronics housing 30.

The instrument 10 is preferably “plug and play” with respect to theprobes 50 connected to the cylindrical electronics housing 30.Preferably, when instrument 10 is powered “on,” the CPU 34 will test allinputs 32 for the presence of individual sensors or probes 50 anddetermine the type and number of sensors that will be monitored. Forexample, a thermocouple sensor input will be tested whether itselectrical resistance is less than a pre-determined value. For oilpressure and fuel pressure, the sensor input will be tested whethertheir resistance is less than a pre-determined value. For fuel flow andtachometer, the readings from the particular input 32 are tested by theCPU 34 for whether the readings are greater than a pre-determined value.After the CPU software completes the “power on” tests, a configurationof the type and number of sensors connected to the instrument 10 arestored in memory and then output is displayed based on thisconfiguration. In subsequent “power on” cycles, any new sensors/probes50 discovered by the CPU 34 will be added to the stored configuration.If, however, a previously configured sensor/probe 50 is not detected,the CPU will display an error message pertaining to the now missingprobe 50.

Once the probes 50 are connected and detected, the user then can selectthe proper positional mode of display for the display area 22. Using thecontrol buttons (24, 28), the user selects the preferred positional modeof display for the instrument with the method shown in FIG. 9. In FIG.3, the first portrait display mode would be selected (as shown in FIG. 2a.)

Referring to FIG. 9, a flow chart of a preferred method of switchingbetween positional modes of display is shown. To begin the preferredswitching method, the user presses and holds the “STEP” button 24 for anextended period of time, e.g. 8 seconds. Next, the CPU 34 detects theextended press of the button 24 and displays an indicator, e.g. anarrow, on the display 22 indicating the “top” of the current positionalmode of display. Once the indicator is visible to the user, the userdepresses the “LF” button 28. Next, the CPU 34 detects the press of thesecond button 28 and rotates the displayed indicator 90 degrees. If theuser sees that the “top” of the indicator does not correspond to the topof the display position, the user presses the “LF” button 28 again andthe CPU 34 rotates the indicator another 90 degrees. If the user seesthat the indicator is indicating the top of the display position, theuser presses the “STEP” button 24. The CPU 34 detects the press ofbutton 24, removes the indicator from the display 22, and displays thenew positional mode of display thus completing the process.

FIG. 4 shows a rear view of a preferred embodiment of the avionicsinstrument 10 in first portrait display position. The length of thedisplay panel 21 extends below the diameter of the cylindricalelectronics housing 31. The cylindrical electronics housing 30 alsopreferably has multiple inputs 32 for probes 50. In FIG. 4, fourdifferent inputs 32 are shown. The display panel 22 also preferably hasfour holes 23 for screws used to hold the bracket 40. This allows a moreflush fit of the display panel 20 to the aircraft panel 100.

FIG. 5 shows a front view of a preferred embodiment of the mountingbracket 40. First, the bracket 40 preferably has a cylindrical interior42 with a diameter of approximately 3.01 inches. This allows thecylindrical electronics housing 30 to be inserted into (and rotatedwithin) the cylindrical interior 42 of the bracket 40. Preferably, thebracket 40 has an exterior with squared sides 44 and rounded corners 46and a preferred width of 3.1 inches. The exterior also preferably hasadjustment ports 47 and 48 on opposite sides of an adjustment gap 49. Anadjustment screw 45 traverses the ports 47 and 48 and spans theadjustment gap 49. Once the bracket 40 and instrument 10 are installedin a panel 100, the bracket 40 can hold the instrument 10 in place (inthe desired display position) by tightening the adjustment screw 45 toreduce the adjustment gap 49.

FIGS. 5 and 6 show side views of the preferred embodiment of themounting bracket 40. The bracket is preferably 0.375 inches thick andmade from 2024 aluminum. Alternately, silver, gold, brass, copper andother aluminums can be used. The use of metals with high heatconductivity is preferred. By using such metal, a surprising result wasachieved. The heat from the instrument 10 is conducted away from thedisplay panel 20 of the instrument 10 and into the ambient air and/ordispersed throughout the aircraft panel 100. Thus, the user and theinstrument 10 receive protection from an excessively heated displaypanel 20. For example, the surface temperature of the display panel 20has been reduced by approximately 30 degrees (° F.) by using thepreferred mounting bracket 40. Moreover, by using the disclosed mountingbracket 40, the user does not need to install a fan to cool theinstrument 10 and thereby take up additional space on the panel 100 orrequire additional power to operate the fan.

Thus, an improved avionics instrument display and mounting bracket isdescribed above that is more easily positioned in a standard aircraftpanel and cooled without a fan. In each of the above embodiments, thedifferent positions and structures of the present invention aredescribed separately in each of the embodiments. However, it is the fullintention of the inventor of the present invention that the separateaspects of each embodiment described herein may be combined with theother embodiments described herein. Those skilled in the art willappreciate that adaptations and modifications of the just-describedpreferred embodiment can be configured without departing from the scopeand spirit of the invention. Therefore, it is to be understood that,within the scope of the appended claims, the invention may be practicedother than as specifically described herein.

1. An avionics instrument comprising: a cylindrical electronics housingwith a primary dimension attached to a display panel with a primarydimension where the primary dimension of the display panel exceeds theprimary dimension of the cylindrical electronics housing; where thedisplay panel has at least two positional modes of display and aninterface for switching between the at least two positional modes ofdisplay.
 2. The avionics instrument of claim 1 where the display panelhas four positional modes of display.
 3. The avionics instrument ofclaim 1 where the display panel has a landscape positional mode ofdisplay and a portrait positional mode of display.
 4. The avionicsinstrument of claim 1 where the cylindrical electronics housing has acenter and the display panel has a center offset from the center of thecylindrical electronics housing.
 5. The avionics instrument of claim 1where the primary dimension of the cylindrical electronics housing isless than 3.0 inches and the primary dimension of the display panelexceeds 3.0 inches.
 6. The avionics instrument of claim 1 furthercomprising a CPU connected to at least two sensors that detects inputfrom said sensors and configures the at least two positional modes ofdisplay based on said input.
 7. An avionics instrument metal mountingbracket comprising: a cylindrical interior; an exterior where one sideof the exterior has first and second adjustment ports on opposing sidesof an adjustment gap in the one side; an adjustment screw inserted intothe first and second ports and spanning the adjustment gap; and, a frontface having at least one panel screw port.
 8. The avionics instrumentmetal mounting bracket of claim 7 where the metal mounting bracketcomprises aluminum.
 9. The avionics instrument metal mounting bracket ofclaim 7 where the metal for the mounting bracket is selected from thegroup consisting of gold, silver, copper, aluminum and brass.
 10. Theavionics instrument metal mounting bracket of claim 7 where the exteriorhas squared sides and radiused corners and the front face has four panelscrew ports.
 11. An avionics instrument and mounting bracket comprising:a mounting bracket having a cylindrical interior, an exterior where oneside of the exterior has first and second ports on opposing sides of anadjustment gap in the one side, an adjustment screw inserted into thefirst and second ports and spanning the adjustment gap; and, a frontface having at least one panel screw port; an avionics instrument,having a cylindrical electronics housing with a primary dimension,attached to a display panel with a primary dimension where the primarydimension of the display panel exceeds the primary dimension of thecylindrical electronics housing; where the display panel has at leasttwo positional modes of display and a control button for switchingbetween the at least two positional modes of display; where thecylindrical electronics housing is pivotally inserted into thecylindrical interior of the mounting bracket and held by tightening theadjustment screw.
 12. The avionics instrument and mounting bracket ofclaim 11 where the display panel has four positional modes of display.13. The avionics instrument and mounting bracket of claim 11 where thecylindrical electronics housing has a center and the display panel has acenter offset from the center of the cylindrical electronics housing.14. The avionics instrument and mounting bracket of claim 11 where themounting bracket is made from a metal selected from the group consistingof gold, silver, copper, aluminum and brass.
 15. The avionics instrumentand mounting bracket of claim 11 where the display panel has a landscapepositional mode of display and a portrait positional mode of display.